Abstract: This paper presents the structure design and the validation of satellites in self-series launch mode, as well as the vibration test strategy and the concave control criterion, A new method is proposed to obtain the dural satellite interface loads, and its application in the sinusoidal vibration test of all electric propulsion dual satellites system are reviewed. The test results show that the method can efficiently deduce the interface loads between dural satellites. The method can be applied in the sinusoidal vibration test of other large spacecraft with serveral modules.